一种大型轴流压缩机稳定性与效率的优化方法

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中图分类号：V211.74 文献标志码：A 文章编号：2095-2945（2025）26-0044-04

Abstract：Large-scaleaxialflowcompresorsarewidelyusedinmetallurgywindtunnelsandotherscenarios.Amongthem， thispaperproposesanewmethodbasedonmodulardesignandintegratedoptimizationtoscientificallyoptimizetheflowchanel structureoftheompresorsignificantlyimproveteerodyamiceficiencyndpresureratioaginofteompresodsolve theproblemofstabilityandhigheficiencyofthecompresoroverawideoperatingrange.Atthesametime，numericalsimulation technologyisusedtooptimizetheairflowuniformityintheinletandexhaustchambers，reducing pressrelosses.Experimental resultsshowthattheshaftvibrationanddisplacementofthecompresorarefarlowerthanthealamvalues，thespeedcontrol accuracymeetsthedesignrequirements，andthesealingprformanceisgood.Basedontheaboveresearchesults，itisshownthat thedesignmethodproposedinthispapercannotonlysignificantlyimprovetheaerodynamicperformanceandoperatingstabilityof thecompresor，butalsoaccuratelycontroltheaiflowparametersTheresearchresultscanbeapplied’tothedesignand optimization of continuous transonic wind tunnels，providing reliable technical supportforaircraft aerodynamicresearch.

Keywords：large-scaleaxialcompressor;stability;eficiency;airflowparameter;numerical simulationtechnology

随着航空航天技术快速发展，跨声速风洞作为飞行器气动性能测试的重要工具，其性能直接影响到飞行器设计的精确性，连续式跨声速风洞因其能够提供稳定的气流条件，成为现代气动实验研究中的关键设备。（剩余5995字）